Additive manufacturing methods for forming high-temperature composite structures and related structures
Methods for fabricating high-temperature composite structures (e.g., structures comprising carbon-carbon composite materials or ceramic composite matrix (CMC) materials and configured for use at temperature at or exceeding about 2000° F. (1093° C.)) include forming precursor structures by additive manufacturing (“AM”) (e.g., “3D printing”) with a filament drawn from a spool. The precursor structures are exposed to high temperatures to pyrolyze a precursor matric material of the initial 3D printed structure. A liquid resin is used to impregnate the pyrolyzed structure, to densify the structure into a near-net final shape. Use of expensive and time-consuming molds and post-processing machining may be avoided. Large, unitary, integrally formed parts conducive for use in high-temperature environments may be formed using the methods of the disclosure.
1. A method for forming a composite structure, the method comprising:
forming a precursor structure, comprising:
drawing a filament from a spool on which the filament is wound to deposit an amount of filament material; and
drawing more of the filament from the spool to deposit an additional amount of the filament material on the amount of the filament material,
the filament material comprising a precursor matrix material having embedded therein a reinforcing material; and
heating the precursor structure to solidify at least some of the precursor matrix material and form an intermediate structure;
impregnating the intermediate structure with a liquid resin to add carbon or ceramic material to the intermediate structure and form a densified structure; and
heating the densified structure at a temperature between about 932° F. and about 5432° F.
2. The method of claim 1 , wherein impregnating the intermediate structure with the liquid resin comprises impregnating the intermediate structure with a liquid preceramic polymer precursor material.
3. The method of claim 1 , wherein impregnating the intermediate structure with the liquid resin comprises impregnating the intermediate structure with a liquid organic precursor material comprising carbon.
4. The method of claim 1 , wherein drawing the filament and drawing the more of the filament from the spool comprises passing the filament and the more of the filament through at least one nozzle.
5. The method of claim 1 , wherein forming the precursor structure comprises orienting the reinforcing material along a non-horizontal axis.
6. The method of claim 1 , wherein, in forming the precursor structure, the reinforcing material embedded in the precursor matrix material of the filament material is a continuous fiber material.
7. The method of claim 1 , wherein, in forming the precursor structure, the reinforcing material embedded in the precursor matrix material of the filament material comprises discrete strands of a fiber material.
8. The method of claim 1 , further comprising repeating the impregnating and the heating at least one additional time.
9. A method of forming a high-temperature carbon-carbon or ceramic matrix composite structure, the method comprising:
operating a robotic 3D printing machine to form a 3D precursor structure defining at least one void between substantially-nonporous portions, the operating comprising:
drawing a filament from a spool on which the filament is wound to deposit an amount of filament material, the filament material comprising a precursor matrix material having embedded therein a fiber reinforcing material;
laying the filament along an axis; and
drawing more of the filament from the spool to deposit an additional amount of the filament material on the amount of the filament material;
pyrolyzing the 3D precursor structure at a temperature exceeding about 932° F. to solidify at least some of the precursor matrix material and form a porous intermediate structure;
introducing, into pores of the porous intermediate structure, a liquid resin comprising carbon or a preceramic material to impregnate the porous intermediate structure with the liquid resin to add the carbon or a ceramic material to the porous intermediate structure and form a densified and impregnated intermediate structure; and
heating the densified and impregnated intermediate structure at a temperature between about 932° F. and about 5432° F.
10. The method of claim 9 , lacking use of a prefabricated mold.
11. The method of claim 9 , wherein:
drawing the filament from the spool comprises drawing the filament from the spool through a nozzle of the robotic 3D printing machine; and
laying the filament along the axis comprises directing the nozzle of the robotic 3D printing machine along a horizontal direction.
12. The method of claim 9 , wherein:
pyrolyzing the 3D precursor structure at the temperature exceeding about 932° F. comprises pyrolyzing the 3D precursor structure at a temperature exceeding about the 932° F., up to about 5432° F.
13. The method of claim 9 , further comprising, after heating the densified and impregnated intermediate structure at the temperature between about 932° F. and about 5432° F., impregnating with more of the liquid resin.
14. A composite structure, formed by the method of claim 1 , the composite structure comprising:
an intermediate portion, defining a series of cells, between an upper portion and a lower portion,
the intermediate portion, the upper portion, and the lower portion each comprising a composite material comprising the reinforcing material embedded within a matrix phase formed from the precursor matrix material,
the intermediate portion, the upper portion, and the lower portion being integral with one another.
15. The composite structure of claim 14 , wherein the matrix phase comprises a carbon-based material.
16. The composite structure of claim 14 , wherein the matrix phase comprises a ceramic material.
17. The composite structure of claim 14 , wherein the upper portion and the lower portion define at least partially planar, continuous surfaces.
18. The composite structure of claim 14 , wherein the composite structure comprises at least a portion of a structure of a rocket nozzle, a thermal protection system (TPS), or a vehicle configured to travel at speeds of at least about Mach 5.
19. The composite structure of claim 14 , wherein the composite material of the intermediate portion, the upper portion, and the lower portion is substantially non-porous.
20. The composite structure of claim 14 , wherein the composite material comprises solid carbon or solid ceramic material within pores of the matrix phase.